CN111765058B - Cusp field thruster for microwave-enhanced auxiliary ionization - Google Patents
Cusp field thruster for microwave-enhanced auxiliary ionization Download PDFInfo
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- CN111765058B CN111765058B CN201910259148.XA CN201910259148A CN111765058B CN 111765058 B CN111765058 B CN 111765058B CN 201910259148 A CN201910259148 A CN 201910259148A CN 111765058 B CN111765058 B CN 111765058B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H—PRODUCING A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
- F03H1/00—Using plasma to produce a reactive propulsive thrust
- F03H1/0081—Electromagnetic plasma thrusters
Abstract
The invention provides a cusp field thruster for microwave-enhanced auxiliary ionization, belongs to the field of electric thrusters, and particularly relates to a cusp field thruster for microwave-enhanced auxiliary ionization. The problems of insufficient working medium utilization rate, low efficiency, low adjusting precision and the like which are difficult to overcome in the miniaturization process of the tangential field thruster are solved. The device comprises an SMA microwave input interface, an anode, an air supply pipe, a resonant antenna, a permanent magnet ring, a discharge channel, a microwave resonant cavity and a magnetic tip magnetic ring. The microwave-enhanced auxiliary ionization device is mainly used for microwave-enhanced auxiliary ionization of the cusp field thruster.
Description
Technical Field
The invention belongs to the field of electric thrusters, and particularly relates to a cusp field thruster for microwave enhanced auxiliary ionization.
Background
The electric propulsion system has the advantages of higher thrust, high efficiency and long service life, receives more and more attention in space missions and gradually replaces the traditional chemical propulsion. In recent years, the rise of micro-nano satellites and a new-generation space science task have further demands on low thrust, low noise and high vector precision thrust. However, since the radio frequency ion thruster, the field emission thruster, the colloid thruster and the cold air thruster, which are the mainstream in the world, have the key problems of high complexity, narrow adjustable range, short service life and the like, it is necessary to develop a novel micro thruster.
The cusp field thruster is a novel electric propulsion concept appearing internationally, and has the advantages of low complexity, wide adjustable range, low noise and long service life due to the special magnetic field position type. The operating principle is that a cusped magnetic field is arranged in a ceramic channel of the cusped field thruster, most of the magnetic field is parallel to the wall surface except a magnetic tip, electrons mainly do spiral drifting motion along magnetic lines of force, and the electrons are difficult to cross the magnetic field and reach the wall surface. The particles rebound under the action of the magnetic mirror force until the particles collide with neutral particles to be ionized, and the generated ions are ejected out of the channel under the action of the axial electric field and are neutralized with electrons to generate thrust. However, the research on the miniaturized cusp field thruster finds that the thruster still has two defects: firstly, the thruster is undersized, so that the ionization space is insufficient, and the working medium utilization rate is low; secondly, the thrust can only be adjusted by flow and voltage, the adjusting means is less, and the adjusting precision is not high.
Disclosure of Invention
The invention provides a cusp field thruster for microwave enhanced auxiliary ionization, aiming at solving the problems in the prior art.
In order to achieve the purpose, the invention adopts the following technical scheme: a microwave-enhanced auxiliary ionization cusp field thruster comprises an SMA microwave input interface, an anode, an air supply pipe, a resonant antenna, permanent magnet rings, a discharge channel, a microwave resonant cavity and a magnetic tip magnetic conduction ring, wherein the SMA microwave input interface is connected with the outer bottom surface of the microwave resonant cavity and is of an integrated structure, an SMA interface insulating medium is filled in a cavity of the SMA microwave input interface, the anode is arranged on the inner bottom surface of the microwave resonant cavity, the anode and the microwave resonant cavity are mutually insulated through an anode insulating sleeve, the resonant antenna penetrates into the microwave resonant cavity from the SMA microwave input interface end and is fixed at the axis of the microwave resonant cavity, the side wall of the microwave resonant cavity is connected with the air supply pipe to supply a neutral gas working medium into the microwave resonant cavity, the discharge channel is coaxially connected with the microwave resonant cavity, the outer wall of the discharge channel is sleeved with three permanent magnet rings, and the magnetic tip magnetic conduction rings are respectively arranged between the adjacent permanent magnet rings, the magnetizing directions of the three permanent magnetic rings are axial, and the polarity directions of the three permanent magnetic rings are NS-SN-NS or SN-NS-SN.
Furthermore, the outer wall of the microwave resonant cavity is sleeved with an insulating compensation ring, the insulating compensation ring is connected with the thruster bottom plate and the thruster shell, the thruster bottom plate is fixedly connected with the thruster shell through a bolt, the inner wall of the thruster shell is connected with the permanent magnetic ring and the magnetic tip magnetic conduction ring, the outlet of the thruster shell is fixedly connected with the thruster top plate through a bolt, and the air supply pipe penetrates through the thruster shell and the insulating compensation ring and then is connected with the side wall of the microwave resonant cavity.
Furthermore, the SMA microwave input interface, the anode, the thruster bottom plate, the resonant antenna, the thruster shell and the microwave resonant cavity are made of non-magnetic materials or weak magnetic materials.
Furthermore, the insulating compensation ring, the discharge channel, the thruster top plate and the anode insulating sleeve are all made of boron nitride ceramic materials.
Furthermore, the magnetic tip magnetic conduction ring is made of electrical pure iron DT4C material.
Furthermore, the neutral gas working medium is xenon or krypton.
Compared with the prior art, the invention has the beneficial effects that: according to the invention, by feeding microwaves into the upper stream of the channel of the thruster, electrons captured in the magnetic field form cyclotron resonance between the antenna and the resonant cavity, the ionization action of the upper stream of the discharge channel is enhanced, the service life of the cusp field thruster is kept, the working medium utilization rate and the overall efficiency of the thruster are greatly improved, the full ionization and acceleration of the thruster under low working medium density and low power are realized, the efficiency and the specific impulse of the thruster are improved, and the performance of the cusp field thruster is improved. Meanwhile, a thruster regulation and control means for regulating the ionization process by microwaves is introduced, so that the thruster can realize effective regulation of the working condition of the thruster by changing parameters such as power, frequency and the like of input microwaves, and more choices are provided for on-satellite thrust regulation strategies. Compared with the conventional mainstream small electric propulsion system, the thruster has the advantages in service life, system complexity and overall performance.
Drawings
FIG. 1 is a schematic cross-sectional structure diagram of a cusp field thruster for microwave-enhanced assisted ionization according to the present invention
FIG. 2 is a schematic view of a three-dimensional structure of a cusp field thruster for microwave-enhanced assisted ionization according to the present invention
FIG. 3 is a front top view of a cusp field thruster with microwave enhanced assisted ionization according to the present invention
FIG. 4 is a schematic cross-sectional three-dimensional structure diagram of a cusp field thruster for microwave-enhanced assisted ionization according to the present invention
FIG. 5 is a schematic diagram of a cusped field thruster for microwave-enhanced assisted ionization according to the present invention
1-SMA microwave input interface, 2-SMA interface insulating medium, 3-anode, 4-thruster bottom plate, 5-insulating compensation ring, 6-air supply pipe, 7-resonant antenna, 8-permanent magnetic ring, 9-thruster shell, 10-discharge channel, 11-microwave resonant cavity, 12-magnetic tip magnetic conduction ring, 13-thruster top plate, 14-anode insulating sleeve
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely explained below with reference to the drawings in the embodiments of the present invention.
Referring to fig. 1-5 to illustrate the present embodiment, a microwave-enhanced auxiliary ionization cusp field thruster includes an SMA microwave input interface 1, an anode 3, an air supply pipe 6, a resonant antenna 7, a permanent magnet ring 8, a discharge channel 10, a microwave resonant cavity 11, and a magnetic tip magnetic ring 12, where the SMA microwave input interface 1 is connected to the outer bottom surface of the microwave resonant cavity 11 and is an integrated structure, a cavity of the SMA microwave input interface 1 is filled with an SMA interface insulating medium 2, the anode 3 is installed on the inner bottom surface of the microwave resonant cavity 11, the anode 3 and the microwave resonant cavity 11 are insulated from each other by an anode insulating sleeve 14, the resonant antenna 7 penetrates from the SMA microwave input interface 1 end to the inside of the microwave resonant cavity 11 and is fixed at the axis of the microwave resonant cavity 11, the side wall of the microwave resonant cavity 11 is connected to the air supply pipe 6 for a neutral gas working medium to enter the microwave resonant cavity 11, the discharge channel 10 is coaxially connected with the microwave resonant cavity 11, the outer wall of the discharge channel 10 is sleeved with three permanent magnetic rings 8, magnetic tip magnetic rings 12 are arranged between the adjacent permanent magnetic rings 8, the magnetizing directions of the three permanent magnetic rings 8 are axial, and the polarity directions of the three permanent magnetic rings 8 are NS-SN-NS or SN-NS-SN.
When the cusp field thruster described in this embodiment operates, a neutral gas working medium enters the microwave resonant cavity 11 through the gas supply pipe 6, a microwave source feeds microwaves into the resonant antenna 7 through the SMA microwave input interface 1, the microwave frequency and electrons in a magnetic field in the microwave resonant cavity 11 generate electron cyclotron resonance, microwave energy is fed into the electrons to ionize the microwave resonant cavity 11, the positive electrode of the dc power supply is connected with the anode 3 through the power supply line, a high potential is applied to the anode 3, the neutral gas working medium and plasma generated in the microwave resonant cavity 11 enter the discharge channel 10 to collide with the electrons under the action of the cusp magnetic field to form sufficient ionization, and the axial electric field generated by the anode 3 accelerates and ejects to form thrust. When the cusp field thruster operates, effective and accurate flow control can be realized by adjusting input parameters of microwaves, actual operation is carried out according to different requirements, the input power of the microwaves is improved, the temperature of electrons in the microwave resonant cavity 11 is increased, and the ionization intensity and the proportion of high-valence ionized ions in the microwave resonant cavity 11 are changed; by adjusting the input frequency of the microwave, electrons with different cyclotron frequencies generate cyclotron resonance, and the spatial distribution of an ionization region in the microwave resonant cavity 11 is changed.
In this embodiment, the outer wall of the microwave resonant cavity 11 is sleeved with an insulating compensation ring 5, the insulating compensation ring 5 is connected with both a thruster bottom plate 4 and a thruster housing 9, the thruster bottom plate 4 and the thruster housing 9 are fixedly connected through bolts, the inner wall of the thruster housing 9 is connected with both a permanent magnetic ring 8 and a magnetic tip magnetic ring 12, the outlet of the thruster housing 9 is fixedly connected with a thruster top plate 13 through bolts, the air supply pipe 6 penetrates through the thruster housing 9 and the insulating compensation ring 5 and then is connected with the side wall of the microwave resonant cavity 11, the SMA microwave input interface 1, the anode 3, the thruster bottom plate 4, the resonant antenna 7, the thruster housing 9 and the microwave resonant cavity 11 are made of non-magnetic conductive materials or weak magnetic conductive materials, such as 303 stainless steel, 1060 aluminum alloy and the like, the insulating compensation ring 5, the discharge channel 10, the thruster top plate 13 and the anode insulating sleeve 14 are made of boron nitride ceramic materials, the magnetic tip magnetic conduction ring 12 is made of electrician pure iron DT4C, and the neutral gas working medium of the thruster is xenon or krypton.
The cusp field thruster for microwave enhanced assisted ionization provided by the invention is described in detail, a specific example is applied in the text to explain the principle and the implementation mode of the invention, and the description of the above example is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.
Claims (6)
1. A cusp field thruster for microwave enhanced auxiliary ionization is characterized in that: the device comprises an SMA microwave input interface (1), an anode (3), an air supply pipe (6), a resonant antenna (7), a permanent magnet ring (8), a discharge channel (10), a microwave resonant cavity (11) and a magnetic tip magnetic conduction ring (12), wherein the SMA microwave input interface (1) is connected with the outer bottom surface of the microwave resonant cavity (11) and is of an integrated structure, an SMA interface insulating medium (2) is filled in a cavity of the SMA microwave input interface (1), the anode (3) is installed on the inner bottom surface of the microwave resonant cavity (11), the anode (3) and the microwave resonant cavity (11) are mutually insulated through an anode insulating sleeve (14), the resonant antenna (7) penetrates through the inside of the microwave resonant cavity (11) from the end of the SMA microwave input interface (1) and is fixed at the axle center of the microwave resonant cavity (11), and the side wall of the microwave resonant cavity (11) is connected with the air supply pipe (6), supply neutral gas working medium to get into microwave cavity (11), discharge passageway (10) and microwave cavity (11) are coaxial continuous, three permanent magnetism ring (8) are cup jointed to discharge passageway (10) outer wall, all install magnetism point end magnetic ring (12) between adjacent permanent magnetism ring (8), the direction of magnetizing of three permanent magnetism ring (8) is the axial, the polarity direction of three permanent magnetism ring (8) is NS-SN-NS or SN-NS-SN.
2. The cusp field thruster of microwave enhanced assisted ionization according to claim 1, wherein: microwave cavity (11) outer wall cup joints insulating compensating ring (5), insulating compensating ring (5) all links to each other with thruster bottom plate (4) and thruster shell (9), through bolt fixed connection between thruster bottom plate (4) and thruster shell (9), thruster shell (9) inner wall all links to each other with sharp magnetic conduction ring (12) of magnetic tip with permanent magnetism ring (8), thruster shell (9) exit links to each other through bolt fastening with thruster roof (13), air supply pipe (6) link to each other with microwave cavity (11) lateral wall after running through thruster shell (9) and insulating compensating ring (5).
3. A cusp field thruster for microwave enhanced assisted ionization according to claim 2, characterized in that: the SMA microwave input interface (1), the anode (3), the thruster bottom plate (4), the resonant antenna (7), the thruster shell (9) and the microwave resonant cavity (11) are all made of non-magnetic materials or weak magnetic materials.
4. A cusp field thruster for microwave enhanced assisted ionization according to claim 2, characterized in that: the insulating compensation ring (5), the discharge channel (10), the thruster top plate (13) and the anode insulating sleeve (14) are all made of boron nitride ceramic materials.
5. The cusp field thruster of microwave enhanced assisted ionization according to claim 1, wherein: the magnetic tip magnetic conduction ring (12) is made of electrician pure iron DT4C material.
6. The cusp field thruster of microwave enhanced assisted ionization according to claim 1, wherein: the neutral gas working medium of the thruster is xenon or krypton.
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